EP2101041A2 - Plaque de pulvérisation pour un distributeur d'air de refroidissement d'un moteur à turbine à gaz - Google Patents

Plaque de pulvérisation pour un distributeur d'air de refroidissement d'un moteur à turbine à gaz Download PDF

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Publication number
EP2101041A2
EP2101041A2 EP09250679A EP09250679A EP2101041A2 EP 2101041 A2 EP2101041 A2 EP 2101041A2 EP 09250679 A EP09250679 A EP 09250679A EP 09250679 A EP09250679 A EP 09250679A EP 2101041 A2 EP2101041 A2 EP 2101041A2
Authority
EP
European Patent Office
Prior art keywords
air
cooling air
splash plate
air deflector
aperture
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP09250679A
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German (de)
English (en)
Other versions
EP2101041A3 (fr
EP2101041B1 (fr
Inventor
Tracy A. Propheter-Hinckley
Charles C. Wu
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
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Publication of EP2101041A3 publication Critical patent/EP2101041A3/fr
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Publication of EP2101041B1 publication Critical patent/EP2101041B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Definitions

  • the disclosure generally relates to gas turbine engines.
  • Turbine vanes of some gas turbine engines are cooled by air that is routed toward the vanes by a conduit.
  • the conduit transports the cooling air along a path that is radially outboard of the vanes. Cooling air from the conduit is provided to an annular manifold that distributes the air among the vanes.
  • an exemplary embodiment of a cooling air manifold splash plate for a gas turbine engine comprises: a base having an aperture; and an air deflector supported by the base, the air deflector being positioned relative to the base to receive, from the aperture, a radial flow of gas turbine engine cooling air, the air deflector being operative to redirect at least some of the air received circumferentially.
  • An exemplary embodiment of an assembly for a gas turbine engine comprises: a cooling air conduit having an opening, the cooling air conduit being operative to deliver a flow of cooling air through the opening; and a splash plate having an air deflector positioned outside the opening and in a flow path of the flow of cooling air, the air deflector being operative to redirect at least some of the cooling air circumferentially.
  • An exemplary embodiment of a gas turbine engine comprises: a compressor; a turbine operative to drive the compressor, the turbine having stationary vanes; and a cooling air assembly operative to provide cooling air to the vanes, the cooling air assembly having a cooling air conduit and a splash plate, the cooling air conduit having an opening and being operative to deliver a flow of cooling air through the opening, the splash plate having an air deflector positioned outside the opening and in a flow path of the flow of cooling air, the air deflector being operative to redirect at least some of the cooling air circumferentially such that the cooling air is available for delivery to the vanes.
  • such a splash plate is used to direct air from a cooling air conduit so that the cooling air spreads circumferentially within a manifold that is used to provide the cooling air to cooling passages of turbine vanes.
  • air provided from a cooling air conduit may have a tendency to provide more cooling air flow to vanes located in a vicinity of an opening of the cooling air conduit than to vanes displaced from the opening unless such a splash plate is used.
  • FIG. 1 depicts an exemplary embodiment of a gas turbine engine.
  • engine 100 is depicted as a turbofan that incorporates a fan 102, a compressor section 104, a combustion section 106 and a turbine section 108.
  • cooling air assembly 110 that provides cooling air for several turbine vanes.
  • cooling air assembly 110 provides cooling air for cooling the second stage vanes (e.g., vane 112) of high pressure turbine 114.
  • turbofan gas turbine engine Although depicted as a turbofan gas turbine engine, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of engines, such as steam turbine engines and other configurations of gas turbine engines, e.g., industrial gas turbine engines. Further, the concepts are not limited to use with second stage vanes.
  • cooling air assembly 110 incorporates a cooling air conduit 120, a manifold 122 and a splash plate 124.
  • the cooling air conduit 120 includes an opening 126 through which cooling air is delivered to the manifold 122.
  • Splash plate 124 includes an air deflector 128 that is positioned in a vicinity of opening 126. Specifically, in this embodiment, air deflector 128 is positioned outside of opening 126 and in a flow path of the flow of cooling air (depicted by arrow A). This configuration enables the air deflector to redirect at least some of the cooling air so that the cooling air is distributed circumferentially within manifold 122 and provided to the cooling passages (e.g., passage 130) of the vanes.
  • Splash plate 124 is mounted adjacent to opening 126 of the cooling air conduit by an interference fit formed between a base 140 of the splash plate and portions of manifold 122 and conduit 120 that define a recess 134.
  • Splash plate 124 is shown in greater detail in FIG. 4 , in which it is shown that splash plate 124 includes air deflector 128, base 140 and struts (e.g., strut 142) extending between the base and the air deflector.
  • Air deflector 128 is generally planar and exhibits a major axis 136 that is perpendicular to a longitudinal axis of the engine, and a minor axis 138 that is parallel to the longitudinal axis.
  • Base 140 supports air deflector 128 and includes an aperture 144.
  • Air deflector 128 is spaced from the base and generally extends across a centerline 146 of aperture 144.
  • the air deflector is positioned relative to the base to receive an inwardly directed, radial flow of cooling air that passes through aperture 144. The air deflector then redirects at least some of the air circumferentially, with at least some of the redirected air flowing across the exterior surfaces of the struts.
  • struts 142, 143 and struts 148, 149 are used in splash plate 124.
  • Each of the struts is generally rectangular in shape and extends between an edge 150 of the aperture 144 and an outer periphery 152 of air deflector 128.
  • the struts establish the spacing between the base and the air deflector and, as such, the dimensions of and separation between the struts influence the flow characteristics of the cooling air entering the manifold 122 via the splash plate 124.
  • various other numbers, shapes and/or configurations of struts can be used.
  • cooling air flowing through conduit 120 is expelled from opening 126 so that the cooling air enters manifold 122 after passing splash plate 124.
  • the flow path of the cooling air (which is primarily directed radially inwardly in this embodiment) is redirected in response to encountering the air deflector 128.
  • the air deflector causes at least some of the cooling air to spread circumferentially within the manifold at a distance that is spaced from the cooling passages (e.g., passage 130) of the turbine vanes (e.g., vane 112). This enables the cooling air to spread more evenly within the manifold and into the vanes than may otherwise occur if the splash plate were not present.
  • FIG. 6 is a schematic diagram depicting another exemplary embodiment of a splash plate.
  • splash plate 160 includes an air deflector 162, a base 164 and struts (e.g., strut 166) extending between the base and the air deflector.
  • Air deflector 162 is generally planar and exhibits a major axis 168 that is typically oriented perpendicular to a longitudinal axis of the engine in which the splash plate is installed, and a minor axis 169 that is parallel to the longitudinal axis.
  • the air deflector includes holes (e.g., hole 171) that extend between surfaces 173, 175 of the air deflector. At least some of the holes through the air deflector allow air to be directed to the vanes via line of sight flow paths in contrast to being redirected around the air deflector.
  • Base 164 supports air deflector 162 and includes an aperture 170.
  • Air deflector 162 is spaced from the base and generally extends across a centerline 172 of aperture 170.
  • the air deflector is positioned relative to the base to receive a flow of cooling air that passes through aperture 170. The air deflector then redirects at least some of the air for distribution through an associated manifold, with at least some of the redirected air flowing across the exterior surfaces of the struts.
  • struts 166, 167 and struts 176, 177 are used in splash plate 160.
  • Each of the struts is generally rectangular in shape and extends from an edge 180 of the aperture 170 to an outer periphery 182 of air deflector 162.
  • cooling air (depicted by arrows) flowing through a cooling air conduit 184 is expelled from an opening 186 of the conduit so that the cooling air enters a manifold 188 after passing splash plate 160.
  • the flow path of the cooling air is redirected in response to encountering the air deflector 162.
  • the air deflector causes at least some of the cooling air to spread circumferentially within the manifold prior to entering cooling passages (e.g., passage 190) of the turbine vanes (e.g., vane 192).
  • FIG. 8 is a schematic diagram depicting another exemplary embodiment of a splash plate.
  • splash plate 200 includes an air deflector 202, a base 204 and struts (e.g., strut 206) extending between the base and the air deflector.
  • Air deflector 202 exhibits a major axis 208 that is typically oriented perpendicular to a longitudinal axis of the engine in which the splash plate is installed, and a minor axis 209 that is parallel to the longitudinal axis.
  • Air deflector 202 also includes an intermediate portion 210 that is located between end portions 212, 214. In this embodiment, the intermediate portion exhibits a concave curve toward base 204, with the end portions exhibiting convex curves that assist in redirecting the air impinging upon the air deflector.
  • Base 204 supports air deflector 202 and includes an aperture 220.
  • Air deflector 202 is spaced from the base and generally extends across a centerline 222 of aperture 220.
  • the air deflector is positioned relative to the base to receive a flow of cooling air that passes through aperture 220.
  • the air deflector then redirects at least some of the air for distribution through an associated manifold, with at least some of the redirected air flowing across the exterior surfaces of the struts.
  • the curvature exhibited by the air deflector tends to encourage air flow in a circumferential direction (i.e., toward the ends of the air deflector).
  • FIG. 9 is a schematic diagram depicting another exemplary embodiment of a splash plate.
  • splash plate 230 includes an air deflector 232, a base 234 and struts (e.g., strut 236) extending between the base and the air deflector.
  • Air deflector 232 includes an intermediate portion 240 that is located between end portions 242, 244. In this embodiment, the intermediate portion exhibits a concave curve toward base 204, with the end portions exhibiting convex curves.
  • splash plate 230 includes holes (e.g., hole 246) in the air deflector that extend from side 248 to side 249.
  • Base 234 supports air deflector 232 and includes an aperture 250.
  • Air deflector 232 is positioned relative to the base to receive a flow of cooling air that passes through aperture 250. The air deflector then redirects at least some of the air for distribution through an associated manifold, with at least some of the redirected air flowing across the exterior surfaces of the struts. Notably, the curvature exhibited by the air deflector tends to encourage air flow in a circumferential direction (i.e., toward the ends of the air deflector).
  • FIG. 10 is a schematic diagram depicting another exemplary embodiment of a splash plate.
  • splash plate 260 includes an air deflector 262, a base 264 and a pair of struts 266, 268 that extend between the base and the air deflector.
  • Air deflector 262 includes an intermediate portion 270 that is located between end portions 272, 274. In this embodiment, the intermediate portion exhibits a concave curve toward base 264, with the end portions exhibiting convex curves.
  • Base 264 supports air deflector 262 and includes an aperture 270.
  • Air deflector 262 is positioned relative to the base by struts 266, 268 to receive a flow of cooling air that passes through aperture 270. The air deflector then redirects at least some of the air for distribution through an associated manifold, with at least some of the redirected air flowing across the exterior surfaces of the struts.
  • at least the trailing strut 266 (which is located downstream of strut 268 relative to the core flow of the engine in which the splash plate is mounted) includes holes (e.g., hole 272) through which redirected cooling air also can flow. Such holes can encourage downstream flow of the cooling air within the manifold. In other embodiments, neither, either or both of the struts can incorporate holes.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09250679.9A 2008-03-11 2009-03-11 Plaque de pulvérisation pour un distributeur d'air de refroidissement d'un moteur à turbine à gaz Active EP2101041B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/045,781 US8100633B2 (en) 2008-03-11 2008-03-11 Cooling air manifold splash plates and gas turbines engine systems involving such splash plates

Publications (3)

Publication Number Publication Date
EP2101041A2 true EP2101041A2 (fr) 2009-09-16
EP2101041A3 EP2101041A3 (fr) 2012-10-24
EP2101041B1 EP2101041B1 (fr) 2016-11-16

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Cited By (3)

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Publication number Priority date Publication date Assignee Title
US9194246B2 (en) 2011-09-23 2015-11-24 General Electric Company Steam turbine LP casing cylindrical struts between stages
EP3101228A1 (fr) * 2015-05-08 2016-12-07 United Technologies Corporation Déflecteur de division d'écoulement
US9920643B2 (en) 2014-05-14 2018-03-20 Rolls-Royce Plc Distributor device for cooling air within an engine

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US8529195B2 (en) * 2010-10-12 2013-09-10 General Electric Company Inducer for gas turbine system
US9403208B2 (en) 2010-12-30 2016-08-02 United Technologies Corporation Method and casting core for forming a landing for welding a baffle inserted in an airfoil
US9677472B2 (en) 2012-10-08 2017-06-13 United Technologies Corporation Bleed air slot
US9739171B2 (en) 2012-11-16 2017-08-22 United Technologies Corporation Turbine engine cooling system with an open loop circuit
US9927123B2 (en) * 2013-10-24 2018-03-27 United Technologies Corporation Fluid transport system having divided transport tube
US9803501B2 (en) * 2014-02-14 2017-10-31 United Technologies Corporation Engine mid-turbine frame distributive coolant flow
US10309308B2 (en) * 2015-01-16 2019-06-04 United Technologies Corporation Cooling passages for a mid-turbine frame
DE102016124806A1 (de) * 2016-12-19 2018-06-21 Rolls-Royce Deutschland Ltd & Co Kg Turbinen-Laufschaufelanordnung für eine Gasturbine und Verfahren zum Bereitstellen von Dichtluft in einer Turbinen-Laufschaufelanordnung
US10718267B2 (en) * 2017-12-14 2020-07-21 Rolls-Royce Corporation Turbine engine cooling with substantially uniform cooling air flow distribution
US10738637B2 (en) 2017-12-22 2020-08-11 Raytheon Technologies Corporation Airflow deflector and assembly
US10982546B2 (en) * 2018-09-19 2021-04-20 General Electric Company Flow-diverting systems for gas turbine air separator
FR3089545B1 (fr) * 2018-12-07 2021-01-29 Safran Aircraft Engines Dispositif de refroidissement d’un carter de turbine pour une turbomachine
US11421597B2 (en) * 2019-10-18 2022-08-23 Pratt & Whitney Canada Corp. Tangential on-board injector (TOBI) assembly
US11698005B2 (en) 2020-02-07 2023-07-11 Raytheon Technologies Corporation Flow diverter for mid-turbine frame cooling air delivery
CN114198153B (zh) * 2020-09-17 2024-05-03 中国航发商用航空发动机有限责任公司 涡轮叶片冷却系统及航空发动机
US20220316352A1 (en) * 2021-03-31 2022-10-06 Raytheon Technologies Corporation Flow diverter for mid-turbine frame cooling air delivery
JPWO2024053326A1 (fr) * 2022-09-05 2024-03-14

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GB2019503A (en) 1978-04-20 1979-10-31 Gen Electric Turbine cooling system
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US9194246B2 (en) 2011-09-23 2015-11-24 General Electric Company Steam turbine LP casing cylindrical struts between stages
US9920643B2 (en) 2014-05-14 2018-03-20 Rolls-Royce Plc Distributor device for cooling air within an engine
EP3101228A1 (fr) * 2015-05-08 2016-12-07 United Technologies Corporation Déflecteur de division d'écoulement
US9926789B2 (en) 2015-05-08 2018-03-27 United Technologies Corporation Flow splitting baffle

Also Published As

Publication number Publication date
EP2101041A3 (fr) 2012-10-24
EP2101041B1 (fr) 2016-11-16
US8100633B2 (en) 2012-01-24
US20090232637A1 (en) 2009-09-17

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